JPH10176540A - Axial turbine for turbosupercharger - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an excellent cleaning effect at a low cost by installing a cleaning device for the nozzle ring and rotary blades of the axial turbine of a turbosupercharger in a flow passage while a nozzle is opened, and specify ing the installation position of a nozzle hole. SOLUTION: A cleaning device 20 opened in a flow passage 7 and connected to a measuring/control unit is constituted of a nozzle 21 having at least one nozzle hole 24 and a cleaning medium feed pipe 23, and the nozzle hole 24 is arranged at an optional point on a virtual circular plane 35 passing the center point arranged at an interval (a) from an inside housing wall 11. The interval (a) is obtained from the equation a=[(da +di )/2].p1 , where 5%<=p1 <=S30%. The circular plane 35 is formed in a tangential plane 37 to a parallel plane extended in parallel with the streamline 17 of the exhaust gas flow. The diameter dk of the circular plane 35 is obtained from the equation dk =[(da +di )/2].p2 , where 0%<=p2 <=6%.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an axial flow turbine for a turbocharger, and more particularly, to a turbocharger having a gas inlet housing, a turbine impeller supported by a turbocharger shaft and having rotating blades, and a turbocharger. A flow passage formed in the gas inlet housing for the exhaust gas of the internal combustion engine coupled to the
A nozzle ring disposed in the flow passage upstream of the rotary vane and having an inner diameter and an outer diameter; and a cleaning device disposed further upstream and open in the flow passage and coupled to the measurement and control unit. Wherein the gas inlet housing has outer and inner housing walls,
The present invention also relates to a type of receiving an exhaust gas stream of an internal combustion engine having a plurality of streamlines and further guiding the exhaust gas stream to a rotating blade of a turbine impeller.

[0002]

2. Description of the Related Art The use of exhaust gas turbochargers for increasing the output of internal combustion engines is widespread today. In that case, the exhaust gas turbine of the turbocharger receives the supply of exhaust gas from the internal combustion engine, and its kinetic energy is used for intake and compression of air for the internal combustion engine. Depending on the specific operating conditions and the composition of the fuel used for the operation of the internal combustion engine, fouling of the rotating blades and nozzle rings occurs sooner or later in the exhaust gas turbine, and in particular, the nozzle rings are significantly more fouling. . In heavy oil operation, a dirt layer forms on the nozzle ring, the hardness of which depends on the operating principle of the internal combustion engine. In general, this type of fouling in the area of the nozzle ring leads to a reduction in the efficiency of the turbine and thus to a reduction in the output of the internal combustion engine and to a rise in the temperature of the exhaust gas in the combustion chamber, whereby the internal combustion engine and the turbocharger May be thermally overloaded, and in internal combustion engines,
In particular, the valve may be damaged or broken.

[0003] When a layer of dirt accumulates on the nozzle ring and on the turbine blades of a turbocharger coupled to a four-stroke internal combustion engine, it is expected that the pressure and speed of the turbocharger will increase. As a result, the components of the internal combustion engine as well as the components of the turbocharger are thermally and mechanically subjected to high loads, which likewise leads to damage of the components. An uneven distribution of the dirt layer around the rotating blades of the turbine impeller increases the rotor imbalance, which causes damage to the bearing. Therefore, dirt adhering to the nozzle ring as well as the rotating blades of the turbine impeller must be regularly removed.

[0004] German Patent Publication No. 351582
No. 5 discloses a method and a device for cleaning the rotating blades and nozzle rings of an axial turbine of an exhaust gas turbocharger with inside bearings. The axial turbine comprises a gas inlet housing, the gas inlet housing having an outer housing wall and an inner housing wall, wherein the inner housing wall has a turbine impeller, a shaft and a flow passage. Has helped to cover. The cleaning device comprises a plurality of water injectors located in a gas inlet housing of the axial turbine, the water injectors comprising a nozzle and a water conduit extending into the flow passage. When the contamination of the axial turbine reaches a defined degree of contamination, a cleaning request is detected via the measuring and evaluation unit. In response, water is injected into the flow passage through a nozzle located upstream of the guide vane. The water droplets generated at that time are transported by the exhaust gas flow to guide blades or rotating blades of the axial flow turbine, and the attached dirt is removed from those blades.

However, sufficient cleaning of the stationary guide vanes requires
It can only be obtained if the water droplets impinge as fully as possible on the surface of the guide vanes facing the exhaust gas stream. To that end, the water injectors or nozzles must be distributed evenly over the entire circumference of the axial turbine. This requires a very large number of injectors and nozzles, and therefore such a solution is relatively uneconomical and thus expensive. In addition, the cost for sealing the gas inlet housing increases as the number of nozzles increases. Yet another problem is that the nozzle is located in a flow passage region having a relatively high flow velocity.
This results in a flat water jet reaching only a part of the guide vanes. Therefore, sufficient cleaning is not guaranteed.

[0006]

SUMMARY OF THE INVENTION It is an object of the present invention to provide a cleaning device for the nozzle ring and rotary blades of an axial turbine of a turbocharger, in order to avoid all the disadvantages mentioned above. , So that it is possible to obtain an improved cleaning effect at a lower cost.

[0007]

According to the invention, the object is achieved according to the invention in a device according to the preamble of claim 1, wherein the cleaning device comprises a nozzle with one central axis and at least one nozzle. And a cleaning medium supply conduit. The at least one orifice is located at any one point of an imaginary circular surface defined by a center point and a diameter located at a distance a therefrom upstream of the inner housing wall. The center point of the circular surface lies on a virtual parallel plane to the inner housing wall. This imaginary parallel plane is now upstream of the inner housing wall with a distance a
The interval a is calculated by the following equation.

[0008]

(Equation 4)

In the above equation, da is the outer diameter of the nozzle ring, di is the inner diameter of the nozzle ring, and p1 is a percentage defining the minimum and maximum distance between the inner housing wall and the parallel surface.

[0010] Only one streamline of the exhaust gas flow, formed in a gas inlet housing formed without a nozzle, is orthogonal to this parallel plane. This forms an intersection, at which the center point of the circular surface is located. A tangent plane extends in the direction of the tangent to the parallel plane passing through this intersection. A circular surface is formed in this tangent plane. The diameter dk of the circular surface is calculated by the following equation.

[0011]

(Equation 5)

In the above equation, P2 represents a percentage that affects the magnitude of the diameter dk.

The central axis of the nozzle is arranged perpendicular to the tangent plane, and at least one nozzle of the nozzle is oriented at least approximately parallel to this tangent plane.

In accordance with this provision, the nozzle and thus at least one of the nozzles are provided with a complete spreading and even distribution of the cleaning medium on the nozzle ring and on the rotating blades of the turbine impeller on the basis of the streamline elongation and the flow velocity profile. It is located in a possible area. According to the present invention, the cleaning medium is narrowed in the prior art because the cleaning medium is also injected into a region of the gas inlet housing which is also perpendicular to the gas flow but has a high exhaust gas velocity. For example, the nozzle ring and the rotating blades of the turbine impeller are uniformly sprayed by the cleaning medium over the entire circumference and the blade height. Therefore, if the nozzle is 1
Even though only one is used, an improved cleaning effect is guaranteed.

It is particularly advantageous if the nozzle is provided with one orifice located exactly at the center of the circular surface and the distance a between the inner housing wall and the parallel surface is calculated according to the following equation:

[0016]

(Equation 6)

In this arrangement of nozzles or nozzles, the stream lines are optimally used for a uniform spreading of the cleaning medium,
Therefore, the cleaning of the nozzle ring and the rotating blade is further improved.

It is particularly advantageous if the nozzle has at least one orifice on both sides of the tangent plane and at the same distance from this tangent plane. Each orifice has an ejection surface, in which case the sum of these ejection surfaces on both sides of the tangent plane is of equal size. In addition, the injection surfaces are arranged radially overlapping one another or at least one after the other. This further improves the distribution of the cleaning medium around the nozzle ring as well as over the blade height. Furthermore, such nozzles are cost-effective and have a longer service life than nozzles with only one orifice.

The cleaning medium supply conduit comprises two partial conduits, a fixing member for the first externally connected partial conduit is arranged on the outer housing wall, and the second member conduit is connected to the gas inlet housing. It is advantageous if it is formed inside.

According to this configuration, the axially or radially formed gas inlet housing, including the nozzle and the second partial conduit, is fully assembled. The connection of the first partial conduit, in other words the complete assembly of the cleaning device, takes place without having to intervene again in the gas inlet housing for assembly at a later point in time.

Furthermore, the inner housing wall has a hollow interior and is connected to the outer housing wall via at least one rib formed in the flow passage. The second partial conduit extends inside the rib and extends to the interior of the inner housing wall. To that end, the second partial conduit is cast into the axial gas inlet housing. The nozzle is fixed at the upstream end of the inner housing wall and is connected to the second partial conduit. This arrangement of the second partial conduit avoids the influence of the exhaust gas flow by the cleaning medium supply conduit and significantly increases the service life of the cleaning medium supply conduit. The second partial conduit requires little installation space, which results in the gas inlet housing being formed relatively short in the axial direction. Furthermore, when manufacturing such a gas inlet housing, there is little additional manufacturing cost for the cleaning device.

Alternatively, in other words, in a radial gas inlet housing, the second partial conduit transitions at one end to the nozzle and at the other end extends from the inside to the inner housing wall. I have. The inner housing wall has a fixing member for the second partial conduit. A notch is provided inside the rib, and the first and second partial conduits are connected to the notch. Therefore, after removing the turbocharger from the radial gas inlet housing,
The second partial conduit together with the nozzle can be relatively easily detached from the inner space of the inner housing wall. Thus, the partial conduits can be replaced separately, which leads to a cost reduction.

Furthermore, the second partial conduit can be arranged upstream of the nozzle. This results in additional structural variants, in which the second partial conduit and the nozzle can be mounted or removed from outside.
The required maintenance or repair work of the cleaning device is therefore performed very quickly, so that downtime of the turbocharger and thus of the internal combustion engine is reduced.

[0024]

BRIEF DESCRIPTION OF THE DRAWINGS Several embodiments of the invention will now be described with reference to the drawings, based on a radial or axial gas inlet housing of an axial turbine.

The drawings show only those elements which are important for an understanding of the invention. Of the devices, for example, the internal combustion engine and the compressor side of the turbocharger and the bearing area are not shown. The flow direction of the working medium is indicated by arrows.

The main components of the turbocharger shown only partially are the compressor side and the turbine side provided with the axial turbine 1. The turbocharger is connected on the compressor side as well as on the turbine side to an internal combustion engine designed as a diesel engine.

In the first embodiment, the axial turbine 1 has a radial gas inlet housing 2. The axial turbine further comprises a gas outlet housing 3, a turbine impeller 5 provided with rotating blades 6 and supported by a turbocharger shaft 4, and a flow formed in the gas inlet housing 2 for the exhaust gas of the diesel engine. And a passage 7. Upstream of the rotary blades 6, an outer diameter da and an inner diameter d are provided in the flow passage 7.
The nozzle ring 8 provided with i is arranged. The rotating blades 6 are closed outwardly by a cover ring 9 formed as a diffuser. Gas inlet housing 2
Are provided with outer and inner housing walls 10, 11 which limit the flow passage 7 and have three ribs 12 formed to be flow-friendly.
(Only one of the ribs is shown in FIG. 1). The inner housing wall 11 has a hollow inner chamber 13 and serves to shield the turbine wheel 5 and the turbocharger shaft 4 from the flow passage. The gas inlet housing 2 includes a gas outlet housing 3
A plurality of connecting members 14, which are formed as screws, are arranged for the connection (FIG. 1). The gas inlet housing 2 is provided at its upstream end with a gas inlet flange 15 which serves for connection to an exhaust pipe, not shown, of the diesel engine.

During the operation of the turbocharger, the hot exhaust gases coming from the diesel engine are firstly distributed in the exhaust gas stream 16 having at least approximately circular cross section along a number of streamlines 17 in the radial direction of the axial turbine 1. Into the gas inlet housing 2. By the action of the inner housing wall 11,
The conversion takes place to an annular exhaust gas stream 18 having only one stagnation streamline 19 which impinges perpendicularly on the inner housing wall 11. The annular exhaust gas flow 18 is further guided to the turbine impeller 5 via the flow passage 7. In this case, the role of the nozzle ring 8 arranged upstream is to guide exhaust gas to the rotating blades 6 of the turbine impeller 5 optimally. The turbine impeller driven in this way serves for driving a compressor (not shown) connected thereto. The air compressed in the compressor is used for supercharging, in other words for increasing the power of the diesel engine.

Upstream of the nozzle ring 8, a cleaning device 20 opened in the flow passage 7 is arranged in the gas inlet housing 2. This cleaning device comprises a central axis 22, a cleaning medium supply conduit 23 and a nozzle 21 with a spout 24. The cleaning medium supply conduit 23 is connected to the first partial conduit 25 and the second partial conduit 25.
And a partial conduit 26. The second partial conduit 26 is arranged almost exclusively in the inner chamber 13 of the inner housing wall 11. Inner housing wall 11
Has an aperture 27 at its upstream end. Through this hole 27, a second partial conduit 26 is guided into the flow channel 7, in which it passes to the nozzle 21.

The second partial conduit 26 is connected at its other end to the inner housing wall 11 in one area of the rib 12, for which reason the inner housing wall is connected to the threaded fitting. And the second partial conduit 26 is provided with a corresponding union nut 29. The first partial conduit 25 engages the outer housing wall 10 from the outside, for which purpose the outer housing wall 10 comprises a fixing member 30 which is likewise formed as a threaded fitting, and The first partial conduit 25 has a corresponding union nut 31. Inside the rib, in other words, the first partial conduit 2
A cutout 32 is formed between the first and second partial conduits 26 and communicates with these partial conduits (FIG. 1). Of course, additional securing members can be provided for both partial conduits 25,26.

The injection port 24 of the nozzle 21 has a virtual circular surface 34.
Are arranged at the center point 33. The circular surface 34 is defined by a center point 33 and a diameter dk, which is located upstream of the inner housing wall 11 and spaced from it by a distance a.
The center point 33 of the circular surface 34 is located on a virtual parallel surface 35 with respect to the inner housing wall 11, and the distance a between the virtual parallel surface and the inner housing wall 11 is calculated by the following equation.

[0032]

(Equation 7)

The calculation of the position where the injection port 24 is to be arranged is already performed prior to the installation of the nozzle in the gas inlet housing 2. The corresponding procedure is described in FIG. Interval a
Based on the above-mentioned detection method, the percentage p1
The minimum and maximum distance a between the parallel plane 35 and the inner housing wall 11 is obtained from the above, and the average value is shown in FIG. A single streamline 17 of the exhaust gas flow present in the gas inlet housing 2 formed without the nozzle 21 defines an intersection 36 perpendicular to the parallel plane 35 and at this intersection the center of the circular surface 34 Point 33 is located. Intersection 36
And a tangent plane 37 extends in a tangential direction to the parallel plane 35, in which a circular surface 34 is formed. The diameter dk of the circular surface 34 is calculated from the following equation.

[0034]

(Equation 8)

The central axis 22 of the nozzle 21 is arranged perpendicular to the tangent plane 37, and its nozzle 24 is oriented parallel to the tangent plane 37. Nozzle 24 of nozzle 21
Is located at the center point 33 of the circular surface 34 in the present embodiment (FIGS. 1 and 2), but can of course be located at another arbitrary point 38 on the circular surface 34. (FIG. 3). However, in that case, a slight reduction in the cleaning effect must be accepted.

In order to clarify the arrangement of the injection port 24, FIG. 4 shows the nozzle 21 together with the intersection 36 between the streamline 17 and the parallel surface 35.
Is shown enlarged. As can be seen, the tangent plane 37 passes through the center of the nozzle 24 and the nozzle 2
One central axis 22 extends orthogonally. The nozzle 21 used for this consists of the end of the second partial conduit 26 and a baffle 39 with four fixed ribs 40 arranged in a cross. In this case, the fixing ribs 40 are welded to the partial conduit 26 (FIG. 5). Of course, other suitable nozzles could be used.

The nozzle 21 and its injection port 24 are
The cleaning medium is located in the flow passage area in such a way that it extends completely through the nozzle ring 8 and the rotating blades of the turbine impeller 5 and is thus evenly distributed, based on the extension and the flow velocity profile. Thereby, the nozzle ring 8
And the rotating blades 6 are evenly swept by the cleaning medium around their circumference and the blade height, so that an improved cleaning effect is obtained despite the use of only one nozzle 21.

As a cleaning medium for the nozzle ring 8, a liquid such as, for example, water or a solid substance such as, for example, known cleaning granules is used. However, the nozzle 21 described above is particularly suitable for granules. The cleaning process is monitored by a measuring and control unit 41 connected to the cleaning device and triggered by a valve 42 (FIG. 1). The measuring and control unit 41 is, for example, disclosed in DE 3515
825 can be formed and arranged. Of course, other solutions are possible. For example, instead of the air pressure downstream of the turbocharger, other parameters such as, for example, the exhaust gas temperature of the turbocharger, the charging pressure or the rotational speed are detected and the necessary measuring elements are arranged for this. Is also good. Furthermore, an unbalance based on the contamination of the turbine wheel 5 can be measured as turbocharger vibration and can likewise serve as a parameter.

In the second embodiment, the turbocharger is provided with an axial turbine 1 having an axial gas inlet housing 43 (FIGS. 6 and 7). In this case, the second partial conduit 26 of the cleaning medium supply conduit 23 is inserted into the gas inlet housing 43, in other words exactly into the inner housing wall 11, into one of the ribs 12 and into the outer housing wall 10. It has been cast to. In the flow passage 7, a nozzle 44 having four injection ports 24 is formed. Since the stagnation point streamline 19 is located at the center, the lateral movement of the intersection point 36 is impossible, and as a result, the intersection point and thus the axis 22 of the nozzle 44 are also located on the stagnation point streamline 19 (FIG. 6). As in the first embodiment, the circular surface 34 can be detected in this case as well. In this case, it is needless to say that the nozzle 24 of the nozzle 44 can be arranged at an arbitrary point 38 on the circular surface 34. (FIGS. 8 and 3).

On both sides of a tangent plane 37 passing through the intersection 36, two nozzle holes 24 of the nozzle 44 are arranged at the same intervals with respect to the tangent plane 37. In that case,
The orifices 24 are arranged radially overlapping one another and are oriented parallel to the tangent plane 37 (FIG. 8). Each injection port 24 has an injection surface 46 (FIGS. 9 and 10), in which case the sum of the injection surfaces on both sides of the tangent plane 37 is the same. A male thread 47 is provided at the end of the nozzle 44 on the side opposite to the injection port 24 (FIG. 8), and this male thread corresponds to the corresponding female thread 4 of the inner housing wall 11.
8 is used to fix the nozzle 44.

This nozzle 44 is particularly suitable for the use of a liquid cleaning medium, for example water. This nozzle 4
4 is more cost-effective and more robust than the nozzle 21 used in the first embodiment. Both nozzles 44,
The distribution of the cleaning medium at 21 and thus the cleaning effect is the same.

The difference from the first embodiment is that the second partial conduit 26 is not only formed in the inner housing wall 11 but also extends through the rib 12. The second partial conduit is open in the outer housing wall 10;
And it is connected to the first partial conduit 25 at that location.
For this, the corresponding ribs 12 need to be slightly larger, but the corresponding unions of the screw-in fitting 28 and the second partial conduit 26 which are fixed to the inner housing wall 11 in the first embodiment. The nut 29 is not required (FIGS. 1 and 6). Therefore, the second partial conduit 26 cannot be dissociated in the inner chamber 13 of the inner housing wall 11 and is therefore inserted into the rotating turbine impeller 5.
The risk of breakage of the axial turbine 1 due to the penetration of 6 is eliminated.

The third embodiment also comprises an axial gas inlet housing 43, in which the second partial conduit 26 is arranged upstream of the nozzle 44 (FIG. 1).
1). This partial conduit is therefore connected to the inner housing wall 1
1 is not guided through the inner chamber 13 and therefore the nozzle 4
4 is extremely simple and can be installed or removed from the outside. Of course, such an arrangement is also possible in the radial gas inlet housing 2.

[Brief description of the drawings]

FIG. 1 shows an axial flow turbine with a radial gas inlet housing, partially cut away in the plane of the stagnation streamline, in other words in one plane containing all the points of the stagnation streamline. It is.

FIG. 2 is a partially enlarged view showing a region of an outlet of the nozzle of FIG. 1 in detail.

FIG. 3 is a view of a virtual circular surface in a direction of an arrow III in FIG. 2;

FIG. 4 is an enlarged view of the nozzle shown in FIG.

FIG. 5 is a cross-sectional view of the nozzle taken along line VV of FIG. 4;

FIG. 6 shows an axial turbine with an axial gas inlet housing, partially sectioned in the plane of the stagnation point streamline.

FIG. 7 shows the gas inlet housing according to FIG.
It is the end elevation seen in the direction of I.

FIG. 8 is an enlarged view of the nozzle based on FIG. 6;

FIG. 9 is a cross-sectional view of the nozzle taken along line IX-IX in FIG. 8;

FIG. 10 is a cross-sectional view of the nozzle taken along line XX of FIG. 8;

FIG. 11 shows a gas inlet housing according to another embodiment, partially in cross section, similar to FIG. 6;

[Explanation of symbols]

1 axial turbine, 2 radial gas inlet housing, 3 gas outlet housing, 4 turbocharger shaft, 5 turbine impeller, 6 rotating blade, 7 flow passage, 8 nozzle ring, 9 diffuser cover, 10 outer housing Wall, 11 inner housing wall, 12 rib, 13 inner housing wall inner chamber, 14 coupling member (screw), 15 gas inlet flange, 16 circular exhaust gas flow, 17 streamline, 1
8 Annular exhaust gas flow, 19 Stagnation streamline, 20
Cleaning device, 21 nozzle, 22 central axis, 23
Cleaning medium supply conduit, 24 nozzles, 25 first partial conduit, 26 second partial conduit, 27 holes, 28
Fixing member (threaded fitting), 29 Union nut of second partial conduit, 30 Fixing member (threaded fitting), 31 Union nut of first partial conduit, 3
2 notch, 33 center point, 34 circular surface, 35
Parallel plane, 36 intersection, 37 tangent plane, 38 arbitrary point, 39 deflector, 40 fixing rib, 41
Measurement and control unit, 42 valve, 43 gas inlet housing, 44 nozzle, 46 injection face, 47 male thread, 48 female thread, a spacing, da nozzle ring outer diameter, di nozzle ring inner diameter, dk
Diameter of circular surface, p1, p2 percentage

 ──────────────────────────────────────────────────の Continuing on the front page (72) Inventor Marx Corinck, Lenchau-Klatzstrasse, Switzerland 27 (72) Inventor Jean-Eve Wellow, Switzerland Spreitenbach Shopping Center 13/11

Claims (8)

[Claims] An axial turbine for a turbocharger, comprising:
A gas inlet housing (2, 43), a turbine impeller (5) supported by a turbocharger shaft (4) and having rotating blades (6), and exhaust gas of an internal combustion engine coupled to the turbocharger Gas inlet housing for (2,43)
A nozzle ring (8) disposed in the flow passage (7) upstream of the rotary vane (6) and having an inner diameter and an outer diameter (da, di); A cleaning device (2) located upstream, opening into the flow passage (7) and coupled to the measuring and control unit;
0) and a gas inlet housing (2, 43).
Is provided with outer and inner housing walls (10, 11) and receives an internal combustion engine exhaust gas stream (16) having a number of streamlines (17) and transfers the exhaust gas stream to the rotation of the turbine impeller (5). In the form of further guidance to the vanes (6): a) a cleaning device (20) with only one nozzle (21, 44) having a central axis (22) and at least one orifice (24); B) at least one orifice (24) is located at any point (38) on the virtual circular surface (34) and the circular surface (34) Upstream of the housing wall (11) at a distance (a) from the center point (3)
3) and the diameter (dk), c) the center point (33) of the circular surface (34) lies on a virtual parallel surface (35) to the inner housing wall (11). , The inner housing wall (11) and the center point (3
The interval (a) with 3) is expressed by the following equation: D) one of the streamlines (17) of the exhaust gas stream (16) which can be drawn in the gas inlet housing (2, 43) formed without the nozzles (21, 44) (35)
The center point (33) of the circular surface (34) is arranged at this intersection point. E) The tangent plane (37) to the parallel plane (35) is the intersection point. (3
6) and a circular surface (34) is formed in this tangent plane (37); f) The diameter (dk) of the circular surface (34) is G) the central axis (22) of the nozzle (21, 44) is arranged perpendicular to the tangent plane (37) and the nozzle (2
Axial turbine of a turbocharger, characterized in that at least one orifice (24) of (1,44) is oriented at least approximately parallel to a tangent plane (37). 2. The distance (a) between the inner housing wall (11) and the parallel plane (35) is given by the following equation: And the nozzle (21) has a circular surface (3
The axial turbine according to claim 1, further comprising an injection port (24) arranged at a center point (33) of 4). 3. The nozzle (44) has at least one orifice (24) on either side of the tangent plane (37) and at the same distance therefrom; b) The orifices (24) are radially separated from each other. And / or at least one after the other, and c) each orifice (24) is provided with one injection surface (46)
And the ejection surfaces (4) on both sides of the tangent plane (37)
The axial flow turbine according to claim 1, wherein the sum of (6) is the same. 4. A cleaning medium supply conduit (23) comprising two partial conduits (25, 26); b) a first partial conduit (25) connected to the outer housing wall (10) from the outside. (30)
4. An axial turbine according to claim 1, wherein the second partial conduit (26) is formed inside the gas inlet housing (2, 43). 5. a) The inner housing wall (11) has a hollow inner chamber (13) and the outer housing wall (13) is formed via at least one rib (12) formed in the flow passage (7). B) a second partial conduit (26) extending inside the at least one rib (12) and being connected to the housing wall (10);
5. The inner chamber (1) of (1), which is connected to the nozzle (21, 44) at its upstream end.
An axial flow turbine as described. 6. A second partial conduit (26) is cast in the gas inlet housing (43) and the nozzle (2)
An axial turbine according to claim 5, wherein the (1,44) is fixed to the inner housing wall (11). 7. a) The inner housing wall (11) has a hollow inner chamber (13) and the outer housing wall (13) is formed via at least one rib (12) formed in the flow passage (7). B) a second partial conduit (26) is connected at one end thereof to the nozzle (2).
1) and at the other end reaching from the inside to the inner housing wall (11); c) the inner housing wall (11) is fixed to the fixing member (2) for the second partial conduit (26). 28) and d) a notch (32) is formed inside the rib (12), in which the first and second partial conduits (25, 2) are provided.
The axial turbine according to claim 4, wherein (6) is connected. 8. A nozzle (2) comprising a second partial conduit (26).
5. The axial turbine according to claim 4, which is arranged upstream of (1, 44).